Water injection, cooling and denoising system for rocket launching

Abstract

The invention belongs to the technical field of rocket launching, and particularly relates to a water injection, cooling and denoising system for rocket launching. The system comprises outer water injectors, inner water injectors, a lattice girder, a lower water storage device, two water injection main lead pipes and a head water tank, a launching site is provided with the head water tank, the two water injection main lead pipes are led out from the head water tank and are both connected with the lower water storage device, the outer water injectors and the inner water injectors are arranged on the lower water storage device, the outer water injectors are positioned on two sides of a travel portion of a launching platform and parallel to the travel direction of the launching platform, top ends of the outer water injectors are higher than a platform top of the launching platform, tops ends of the inner water injectors are lower than the platform top of the launching platform, and the lattice girder is used fro supporting the outer water injectors and the inner water injectors. The system is developed aiming at bundled rocket launching technical conditions, and is applicable to occasions such as single-nozzle rocket launching test and simulation test adopting similar heat launching technical conditions.

Description

technical field [0001] The invention belongs to the technical field of rocket launching, and in particular relates to a water spraying cooling and noise reduction system for rocket launching. Background technique [0002] During the rocket launch process, the ablation effect of high-temperature, high-speed, and high-condensation gas flow on launch equipment, launch facilities and rockets has always been one of the engineering and technical problems that plague rocket technicians. When the rocket engine displacement increases and the specific impulse increases, the ablation intensity of the gas flow per unit area of ​​the facilities and equipment increases. In some cases, when the weight of the rocket itself increases, the thrust-to-weight ratio of the fire will decrease, which will prolong the ablation time of the gas flow on the unit area of ​​the facilities and equipment. With the improvement of rocket launch technology requirements for launch support systems and launch f...

AI Technical Summary

Problems solved by technology

In some cases, when the weight of the rocket itself increases, the thrust-to-weight ratio of the fire will decrease, which will prolong the ablation time of the gas flow on the unit area of ​​the facilities and equipment.

With the improvement of rocket launch technology requirements for launch support systems and launch facilities, the original launch support system that only carried the weight of the rocket or filled with components, the level of integration, automation, motorization, and informatization of launch facilities has been greatly improved. The system and the structural scheme of the launch facility have undergone great changes. For example, in order to adapt to the pinning release technology and the filling technology of the service tower at the tail end of the arrow base, the launch platform will use the tail service tower, multi-point leveling support arm, and pinning arm structure. The surface of the platform has changed from a simple rotary structure in the past to a jungle-like convex structure. The launch platform’s ability to conduct gas flow is weakened, and the area of ​​the relative stagnation point increases a lot under the condition of severe gas flow disturbance, which further leads to an increase in the ablation intensity of the gas flow. The ablation time is extended, and the difficulty of thermal protection of the launch platform is also greatly increased

Images